田津津,吴彩霞,李孝检,等.自循环机匣处理对某型柴油机增压器压气机的稳定工况范围及性能影响研究[J].内燃机工程,2023,44(6):1-9.
自循环机匣处理对某型柴油机增压器压气机的稳定工况范围及性能影响研究
Influences of Self-Recirculation Casing Treatment on the Stability Range and Aerodynamic Performance of A Diesel Engine Supercharger Compressor
DOI：10.13949/j.cnki.nrjgc.2023.06.001
关键词:增压器压气机  自循环机匣处理  全通道数值模拟  稳定工况范围  气动性能
Key Words:supercharger compressor  self-recirculation casing treatment  full-channel numerical simulation  stable operating range  aerodynamic performance
基金项目:国家自然科学基金项目（12102298）；中国博士后科学基金项目（2021M702443）；天津市研究生科研创新项目（2021YJSS291）
作者单位E-mail
田津津* 天津商业大学 机械工程学院，天津300134 tianjj@tjcu.edu.cn 
吴彩霞 天津商业大学 机械工程学院，天津300134 15978198492@163.com 
李孝检 天津大学 机械工程学院，天津300350 lixiaojian@tju.edu.cn 
张哲 天津商业大学 机械工程学院，天津300134 zhangzhe@tjcu.edu.cn 
赵祎佳* 天津商业大学 机械工程学院，天津300134 zhaoyijia@tjcu.edu.cn 
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摘要:针对某型柴油机增压器压气机，基于整级全通道数值模拟和正交试验设计方法，研究了自循环机匣处理实现高亚声速压气机扩稳增效的潜力。结果表明：自循环机匣能够在提高设计点气动性能的前提下推迟失稳，但会牺牲堵塞流量。压气机的失稳和堵塞流量分别与叶片前缘及叶片扩压器中的堵塞程度相关。小流量侧自循环机匣通过抽吸叶轮叶顶附近低能流体，缓解堵塞，推迟失稳。但在大流量侧自循环机匣的喷射效应会增大扩压器进口攻角，加剧扩压器叶片流动分离，减小堵塞流量。抽吸效应与喷射效应强度均取决于抽吸槽的位置和宽度，压气机稳定性和堵塞流量与抽吸槽参数的变化基本呈负相关。自循环机匣对气动性能的影响包含两方面：在抽吸槽前，经回流槽流出的流体与主流的掺混及其产生的进口畸变将带来额外的效率和压比损失，适当减小回流槽角度可以降低该损失；在抽吸槽下游，得益于抽吸效应对叶顶流动状态的改善，压气机抽吸槽附近及下游高熵区减小，做功能力增强，气动损失大幅降低。在上述两方面共同影响下，压气机设计点气动性能最终得以提高。
Abstract:For a certain type of diesel engine supercharger compressor， based on the full-channel， whole stage numerical simulation method and orthogonal experiment， the potential of self-recirculation casing treatment （SRCT） for the enhancement of stability and efficiency of high subsonic compressor stage was studied. The results show that the SRCT can delay the instability without reducing the aerodynamic performance of the design point， at the expense of reducing the choke flow rate. The stall and choke flow rates of the compressor are related to the degree of blockage in the blade leading edge and the vaned diffuser， respectively. In the small flow region， the SRCT relieves blockage and delays instability by sucking the low-momentum flow near the shroud. However， in the large flow region， the injection of SRCT increases the incidence angle of diffuser inlet， aggravates the flow separation of the diffuser vanes， and reduces the choke flow rate. Both suction and injection depend on the position and width of the bleeding slot， and the stability and chock flow rate of compressor are negatively correlated to them. The influences of SRCT on aerodynamic performance include two aspects. Upstream the bleeding slot， the mixing of the fluid flowing through the reinjecting slot with the main stream and the resulting inlet distortion will bring additional efficiency and pressure ratio loss， and the loss can be reduced by appropriately reducing the reinjecting slot angle. Downstream the bleeding slot， thanks to the improvement of the flow state near the shroud， the high entropy zone near the bleeding slot and downstream of the compressor is reduced， the blade work capacity is improved， and the aerodynamic loss is greatly reduced. With the above two effects combined， the aerodynamic performance of the compressor at design point can be improved.
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